EP1775441A1 - Vorrichtung zur Aufladung eines Verbrennungsmotors sowie Fahrzeug mit einer solchen Vorrichtung - Google Patents

Vorrichtung zur Aufladung eines Verbrennungsmotors sowie Fahrzeug mit einer solchen Vorrichtung Download PDF

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Publication number
EP1775441A1
EP1775441A1 EP06291459A EP06291459A EP1775441A1 EP 1775441 A1 EP1775441 A1 EP 1775441A1 EP 06291459 A EP06291459 A EP 06291459A EP 06291459 A EP06291459 A EP 06291459A EP 1775441 A1 EP1775441 A1 EP 1775441A1
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EP
European Patent Office
Prior art keywords
pressure turbine
turbine
nozzle
section
high pressure
Prior art date
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Granted
Application number
EP06291459A
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English (en)
French (fr)
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EP1775441B1 (de
Inventor
Jean Frédéric Melchior
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Individual
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F02B37/183—Arrangements of bypass valves or actuators therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/009—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00 having two or more separate purifying devices arranged in series
    • F01N13/0097—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00 having two or more separate purifying devices arranged in series the purifying devices are arranged in a single housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N5/00—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy
    • F01N5/04—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/013—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N2250/00—Combinations of different methods of purification
    • F01N2250/02—Combinations of different methods of purification filtering and catalytic conversion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/007—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel, e.g. at least one pump supplying alternatively
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/60—Fluid transfer
    • F05B2260/601—Fluid transfer using an ejector or a jet pump
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to a supercharging device for an internal combustion engine, of the type comprising a turbine coupled to a compressor, a conduit for supplying the turbine with pressurized gas, a duct for evacuating gases which have been expanded in the turbine, and bypass means of the turbine comprising a bypass duct connecting the supply duct to the exhaust duct.
  • the turbine is supplied with exhaust gas under pressure burned by the engine and uses the energy of these exhaust gases to drive the compressor, which supplies the engine with air fresh under pressure.
  • the turbine is generally sized so that the compressor delivers a desired air pressure at a partial rotational speed of the engine, the speed at which the engine expels a specific flow of exhaust gas to the turbine.
  • the bypass means of the turbine allow the passage of a part of the exhaust gas, hereinafter referred to as derivative gases, directly from the upstream of the turbine to the downstream of the turbine, without passing through the turbine, so as to limit the back pressure upstream of the turbine to the level just necessary to achieve the desired air pressure at the outlet of the compressor.
  • An object of the invention is to provide a supercharging device having improved efficiency, and to increase the proportion of exhaust gas that can be derived.
  • the invention proposes a supercharging device for an internal combustion engine, of the aforementioned type, characterized in that the bypass duct opens into the evacuation duct via an expansion nozzle allowing the gas to be ejected.
  • the bypass duct opens into the evacuation duct via an expansion nozzle allowing the gas to be ejected.
  • derived by the bypass duct in a mixing section of the exhaust duct substantially in the direction and direction of flow in the mixing section of the gases expanded in the turbine, to increase the amount of movement of the gases expanded in the turbine by mixing with the derived gases according to the principle of an aerodynamic ejector, whose propellant flow is constituted by the gases derived by the bypass duct, and the driven flow is taken from the gas expanded in the turbine.
  • the internal combustion engine 6 comprises a supercharging device 8 comprising a low-pressure turbocharger comprising a compressor 12 coupled to a turbine 14, and a high-pressure turbocharger 16 comprising a compressor 18 coupled to a turbine 20.
  • the compressors 12 and 18 are arranged in series, and supply the engine 6 with fresh air under pressure.
  • the compressor 18 is located downstream of the compressor 12.
  • the turbines 14 and 20 are arranged in series, and receive the exhaust gas from the engine 6.
  • the turbine 20 is located upstream of the turbine 14.
  • the fresh air is successively compressed in the compressor 12 and the compressor 18, before being sent into the engine 6.
  • the exhaust gases are successively expanded in the turbine 20, then in the turbine 14.
  • the turbine 20 is fed with gas in a supply duct 26 opening for example into a spiral feed volute 27 of the turbine 20, and discharges the expanded gases into a first discharge duct 28.
  • the turbine 14 is fed with gas in the duct 28, which thus forms the supply duct of the turbine 14, and rejects the expanded gases in a second exhaust duct 30.
  • the duct 28 opens into a supply volute 29 spiral turbine 14.
  • the device 8 comprises a first bypass duct 32 of the turbine 20 feeding in the duct 26, and opening into the duct 28 via a first expansion nozzle 34.
  • the device 8 comprises a second bypass duct 36 of the turbine 14 feeding in the duct 28 upstream of the nozzle 34, and opening into the duct 30 via a second expansion nozzle 38.
  • Each nozzle 34, 38 is defined by an annular channel 39 of revolution about an axis A defining the axis A of the nozzle 34, 38, and converge towards the outlet of the nozzle to a neck, constituting the smallest section of the nozzle 34, 38.
  • the channel 39 is delimited between an inner wall of a convergent tube 40, and a central body 42 disposed inside the tube 40.
  • the section of the neck of each nozzle 34, 38 is adjustable, in order to adjust the flow rate of derivative gas passing through the nozzle 34, 38.
  • each nozzle 34, 38 is mounted to move relative to the tube 40 along the axis A of the nozzle 34, 38 between an advanced position of closure of the nozzle 34, 38, in which the body 42 is in substantially sealed contact with the inner wall of the tube 40, and a retracted position of maximum opening, in which a space is provided between the inner wall of the tube 40 and the body 42.
  • each body 42 is controlled by a linear actuator 43.
  • Each nozzle 34, 38 opens into a section 46, 48 of the corresponding exhaust duct 28, 30.
  • Each section 46, 48 feeds gas expanded in the turbine 20, 14 by an annular channel 49 defined between the inner wall of a flare 46 a, 48 a extending the portion 46, 48 upstream, and a wall outer tube 40 of the nozzle 34, 38.
  • Each section 46, 48 extends substantially rectilinear downstream of the corresponding nozzle 34, 38 substantially along the axis A of the nozzle 34, 38.
  • the nozzles 34, 38 are therefore oriented so as to eject the derived gases in the sections 46, 48 in the direction and direction of flow of the gases in these sections 46, 48.
  • each nozzle 34, 38 is of revolution about its axis A, each section 46, 48 developing downstream about the axis A of the nozzle 34, 38 opening into this section 46, 48.
  • the section 46 opens into the volute 29.
  • the section 48 opens into a diverging diffuser 50 opening for example on exhaust gas treatment means.
  • the total pressure P of gas is equal to the sum of a static static pressure P and a dynamic dynamic pressure P, which is proportional to the density of the gases and to the squared velocity of the gases.
  • the gases from the engine 6 are introduced into the turbine 20 at a total pressure P1, are expanded in the turbine 20 at a total pressure P2, less than P1, are introduced into the turbine 14 at a total pressure P3, are expanded in the turbine 14 at a total pressure P4, less than P3, and sent to the inlet of the diffuser 50 at a total pressure P5.
  • the total pressure P3 is substantially equal to the total pressure P2.
  • a derivative gas stream flows in the pipe 32 from upstream to downstream of the turbine 20, without passing through the turbine 20.
  • the flow of derived gases in the conduit 32 depends on the opening of the nozzle 34. The more the nozzle 34 is open, the greater the proportion of derivative gas is important.
  • the derived gases are ejected by the nozzle 34 in the section 46 with a relaxation and an increase in their momentum resulting from the transformation of their pressure energy into kinetic energy.
  • the derivative gases are ejected with a greater amount of movement than that of the gases expanded in the turbine 20.
  • the dimensions of the section 46 are provided to promote the exchange of momentum.
  • the length L of the section 46 is preferably between 5 and 10 times its diameter D.
  • the gases ejected by the nozzle 34 and a portion of the gases expanded in the turbine 20 are mixed in the section 46 with a momentum exchange, so that the amount of movement of the gases expanded in the turbine 20 is increased, and that the amount of movement of the mixed gases, resulting from the mixing of the gases expanded in the turbine 20 with the gases derived in the conduit 30, is greater than that of the gases expanded in the turbine 20 upstream of the nozzle 34.
  • the nozzle 34 defines with the section 46 an aerodynamic ejector 52 taking a propellant flow of gas (the derivative gases) upstream of the turbine 20 and a driven flow of gas downstream of the turbine 20, and mixing the propellant flow and flow driven with momentum exchange to increase the momentum of the driven flow.
  • a propellant flow of gas the derivative gases
  • the inlet of the turbine 14, the mixed gases have a static P3 static pressure substantially equal to the static pressure static P2 of the gas expanded in the turbine 20, and a dynamic P3 dynamic pressure higher than P2 dynamics of gas expanded in the turbine 20
  • the total pressure P3 is therefore greater than the total pressure P2, and a larger energy can be recovered in the turbine 14.
  • the ejector 52 thus makes it possible to convert the pressure of the derivative gases into kinetic energy, and to use this kinetic energy to increase the inlet pressure of the turbine 14. Thus, a larger energy is recovered in the turbine 14, and the overall efficiency of the supercharging device 8 is improved.
  • This improved efficiency makes it possible to increase the proportion of derivative gases, and to improve the performance of the engine 6, especially in the high speeds, in which the exhaust gas flow rate is much higher than the flow rate required to obtain the pressure of the engine. desired air at the output of the compressor 18.
  • the inner wall of the section 46 is a regulated surface which rests on a circular inlet section of the section 46 located substantially at the outlet of the nozzle 34 , and on the critical inlet section of the feed volute of the turbine 14, and the section 46 constitutes a tangential extension of the volute 29.
  • the invention makes it possible to recover, when the nozzle 34 is open so as to derive 50% of the gases, 1 bar of dynamic pressure, and thus to obtain a total pressure P3 of 4 bars, greater than the total pressure P2.
  • the nozzle 38 defines with the section 48 a second aerodynamic ejector 54 taking a gas propellant flow upstream of the turbine 14 and a driven flow of gas downstream of the turbine 14, and mixing the propellant flow and the flow driven with a momentum exchange.
  • the total pressure P5 is equal to the total pressure P4, and when the body 42 of the nozzle 38 is in the open position, the total pressure P5 is greater at the total pressure P4.
  • the duct 36 is fed into the duct 28 upstream of the ejector 52 and does not disturb the operation of the ejector 52.
  • the nozzle 34 being designed to eject the gas downstream in the section 46, these gases are unlikely to rise towards the entrance of the duct 36.
  • the by-pass means of the turbine 14 make it possible to improve the expansion ratio of the turbine 14, ie the ratio of the total pressure P3 at the inlet of the turbine 14 to the static static pressure P4 at the outlet of the turbine 14.
  • the nozzle 38 when it is open, makes it possible to increase the pressure P5, and a static static pressure P4 that is lower at the outlet of the turbine 14 than when the nozzle 38 is closed in order to obtain in downstream of a pressure P5 sufficient for the flow of gases. Therefore, the expansion rate of the turbine 14 is increased, and the energy recovered by the turbine 14 is larger.
  • the opening of the nozzle 38 thus causes both an increase in the total pressure P3 and a decrease in the static static pressure P4. This makes it possible to improve the energy recovered in the turbine 14, and the efficiency of the device 8.
  • the section of the neck of the nozzle 34 is adjustable between a minimum value, preferably zero, and a maximum value substantially between one and two times the critical section of the turbine 20, and the critical section of the turbine 14 is between two and three times the critical section of the turbine 20.
  • the section 46 is preferably slightly convergent to accelerate the flow of gases to the critical section of the turbine feed volute 14.
  • the section 48 is preferably cylindrical.
  • FIG. 2 differs from the previous embodiment in that the ejector 54 is made, which makes it possible to introduce the gas propellant flow to the outside the driven gas flow.
  • the channel 39 of the nozzle 38 is delimited between an inner wall of a convergent extension 61 of the channel 48 and the outer surface 60 of a cylindrical tubular sleeve 62 of axis A of the nozzle 38, whose inner surface 64 defines a section of the exhaust duct 30 of the turbine 14 extending between the turbine 14 and the mixing section 48.
  • the sleeve 62 is mounted to move relative to the convergent 61 along the axis A of the nozzle 38 under the effect of a linear actuator 43, between a closed position of the nozzle 38, in which a conical end 64 of the sleeve 62 is in substantially sealing contact with the inner wall of the convergent 61, and an open position, in which a space is provided between the inner wall of the convergent 61 and the end 64.
  • the inner wall of the convergent 61 is an upstream extension of an inner wall of the mixing section 48.
  • the body 42 of the nozzle 34 is advantageously extended downstream by a conical tip to ensure continuous evolution of the sections of the duct.
  • the diffuser 50 opens on a radial diffuser 66 which waters exhaust gas treatment means 68, 70, for example a particle filter or a catalyst, annular around the diffuser 50 and the section 48 to preserve the compactness of the engine 6 .
  • the turbine 14 is a radial turbine axis axis A of the nozzle 38, the turbine being radial inlet and axial outlet.
  • the gases leave the turbine 14 advantageously by flowing along the axis A of the nozzle 38 and the section 48.
  • the ejector 52 is of the type of the ejector 54, that is to say that it allows an introduction of the gas propellant flow to the outside of the driven gas flow.
  • the device 8 differs from that of FIG. 2 in that it allows the channel 49 to be closed. supplying the section 46 with gas expanded in the turbine 20.
  • the tube 40 of the nozzle 34 is slidably mounted relative to the casing of the turbine 20, along the axis A of the nozzle 34, between a retracted position in which the channel 39 is closed and the channel 49 is open. and an advanced position in which the outer surface of a front end 72 of the tube 40 is in sealing contact with the inner wall of the flare 46 has, so that the channel 49 is closed, the channel 39 being open.
  • a first half (top in Figure 3) of the tube 40 is shown in the retracted position, and a second half (bottom in Figure 3) of the tube 40 is shown in the advanced position.
  • the central body 42 is fixedly mounted relative to the casing of the turbine 20.
  • the body 42 is carried at the end of a rod 74 secured to the casing of the turbine 20, and the tube 40 is disposed around the body 42, and connected by radial arms 76 to a sleeve 78 slidably mounted on the stem 74.
  • the tube 40 is provided for example with a sealing segment 80 which slides in a cylindrical bore 82 of the casing of the turbine 20.
  • the tube 40 is movable in a plurality of intermediate positions between its retracted position and its advanced position, in order to adjust the openings of the channels 39 and 49.
  • the displacement of the tube 40 is controlled for example by means of a linear actuator (not shown) acting on the sleeve 78.
  • the duct 36 of the turbine 14 comprises an adjustable shutter device 84 constituted by a simple valve 86.
  • the duct 36 is closed off by an adjustable nozzle 38 as described above.
  • the tube 40 In operation, at low engine speed, the tube 40 is in the retracted position, the channel 49 is open and the channel 39 closed, all the gases of the duct 26 are successively relaxed in the turbine 20 and the turbine 14 which operate in series, as illustrated by an arrow C.
  • the duct 36 is closed.
  • the tube 40 When the engine speed increases, the tube 40 is progressively advanced to create an increasing flow of gas derivatives in the channel 39 which accelerate the gas expanded in the turbine 20 discharged into the channel 49.
  • the conduit 36 is kept closed.
  • valve 86 is opened progressively when the tube 40 continues its movement of opening the channel 39 and closing the channel 49. A derived flow thus settles in the duct 36.
  • the latter is rapidly advanced to bring its end 72 in sealing contact with the inner wall of the flare 46a in order to close the channel 49 and open the channel 39 widely.
  • the valve 86 is brought in full opening to allow the gas expanded in the turbine 20 to evacuate in the conduit 36 along the arrow B1.
  • the turbines 14 and 20 then operate in parallel.
  • the turbine 14 is then directly supplied by the conduit 26, via the channel 39, according to the arrow B2.
  • the device of FIG. 3 makes it possible to pass simply and continuously from a pure series configuration to a series configuration with derivation of the high pressure turbine, then to a series configuration with bypass of the high pressure and low pressure turbines to reach to a parallel configuration.
  • This configuration change is made using the single actuator of the movable member (tube 40) of the nozzle 34, which simplifies the control device and reduces the manufacturing cost.
  • the device 8 of FIG. 3 is particularly suitable for the implementation of a two-stage turbocompression process such as that described in FIG. FR 2,853,011 , in which the turbines operate in series below a given regime, and in parallel above this determined regime. Indeed, the device according to Figure 3 improves the efficiency in the configurations where the turbines are in series and partially bypassed.
  • the duct 36 In the advanced position of the tube 40, to allow the appropriate evacuation of the gas expanded in the turbine 20, in the maximum open position of the valve 86, the duct 36 preferably has a section substantially equal to the section of the duct 28.
  • the body 42 is also movable relative to the turbine 20, in order to independently modify the openings of the channels 39 and 49.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)
EP06291459A 2005-09-21 2006-09-18 Vorrichtung zur Aufladung eines Verbrennungsmotors sowie Fahrzeug mit einer solchen Vorrichtung Not-in-force EP1775441B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0509652A FR2891011A1 (fr) 2005-09-21 2005-09-21 Dispositif de suralimentation pour moteur a combustion interne, et vehicule automobile equipe d'un tel dispositif

Publications (2)

Publication Number Publication Date
EP1775441A1 true EP1775441A1 (de) 2007-04-18
EP1775441B1 EP1775441B1 (de) 2008-06-18

Family

ID=36499482

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06291459A Not-in-force EP1775441B1 (de) 2005-09-21 2006-09-18 Vorrichtung zur Aufladung eines Verbrennungsmotors sowie Fahrzeug mit einer solchen Vorrichtung

Country Status (6)

Country Link
US (1) US20070062190A1 (de)
EP (1) EP1775441B1 (de)
JP (1) JP2007100695A (de)
AT (1) ATE398724T1 (de)
DE (1) DE602006001499D1 (de)
FR (1) FR2891011A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009043487A1 (de) * 2007-09-27 2009-04-09 Behr Gmbh & Co. Kg Mehrstufige aufladegruppe, mehrstufige aufladevorrichtung und aufladesystem
WO2009118471A1 (fr) * 2008-02-29 2009-10-01 Melchior Jean-Frederic Moteur a combustion interne a suralimentation pulsee
WO2011060914A1 (de) * 2009-11-20 2011-05-26 Mtu Friedrichshafen Gmbh Mehrstufige aufladegruppe, aufladesystem und brennkraftmaschine, jeweils mit der mehrstufigen aufladegruppe

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US8387385B2 (en) * 2004-08-31 2013-03-05 The United States Of America, As Represented By The Administrator Of The U.S. Environmental Protection Agency Efficient bypass valve for multi-stage turbocharging system
FR2909718B1 (fr) 2006-12-11 2009-02-27 Jean Melchior Moteur a combustion interne suralimente
EP2752565B1 (de) * 2009-03-06 2018-12-12 Toyota Jidosha Kabushiki Kaisha Mehrstufige Turboladungs-Systemsteuerungsvorrichtung
DE102009030482A1 (de) * 2009-06-24 2011-03-24 Benteler Automobiltechnik Gmbh Abgasbaugruppe
GB2475534B (en) * 2009-11-21 2014-11-12 Cummins Turbo Tech Ltd Sequential two-stage turbocharger system
US20110120123A1 (en) * 2009-11-23 2011-05-26 International Engine Intellectual Property Company , Llc Low pressure turbine waste gate for diesel engine having two stage turbocharger
JP5728943B2 (ja) * 2010-12-28 2015-06-03 いすゞ自動車株式会社 ターボシステム及び切替式二段過給機ターボシステム
JP5728942B2 (ja) * 2010-12-28 2015-06-03 いすゞ自動車株式会社 切替式過給機ターボシステム
US20120227400A1 (en) * 2011-03-09 2012-09-13 General Electric Company Method and system for improving efficiency of multistage turbocharger
CN103256108B (zh) * 2013-05-16 2016-01-27 浙江吉利汽车研究院有限公司杭州分公司 一种汽车尾气发电装置
US9546591B2 (en) * 2014-11-26 2017-01-17 Caterpillar Inc. Exhaust system with exhaust gas recirculation and multiple turbochargers, and method for operating same
DE102017201468A1 (de) * 2017-01-31 2018-08-02 Continental Automotive Gmbh Turbolader für eine Brennkraftmaschine
CN108643994B (zh) * 2018-04-28 2020-06-19 湖南大学 一种车载发动机排气能量多级联合回收装置
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DE602006001499D1 (de) 2008-07-31
US20070062190A1 (en) 2007-03-22
EP1775441B1 (de) 2008-06-18
JP2007100695A (ja) 2007-04-19
ATE398724T1 (de) 2008-07-15

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